3052 Federal Register / Vol. 72, No. 15 / Wednesday, January 24, 2007 / Rules and Regulations 

Actions Compliance Procedures 

(2) If cracks are found during the 

inspection required in paragraph 

(e)(1) of this AD in areas A, B, 

and C (as shown in Figure 1 of 

EXTRA Service Bulletin No. 300–

2–95, Issue: F, Dated: July 10, 

2006), weld the crack and modify 

the upper longeron at the horizontal stabilizer attachment by installing the applicable modification kit (or FAA-approved equivalent parts).

For all affected airplanes: Before further flight after the inspection required in paragraph (e)(1) of this AD in which cracks are found, unless already done.Follow Part II of EXTRA Service 

Bulletin No. 300–2–95, Issue: F, 

Dated: July 10, 2006. 

(3) If no cracks are found during 

the inspection required in paragraph (e)(1) of this AD, modify 

the upper longeron at the horizontal stabilizer attachment by installing the applicable modification kit (or FAA-approved equivalent parts).

For all affected airplanes: Within the next 100 hours TIS after February 28, 2007 (the effective date of this AD), unless already done.Follow Part II of EXTRA Service 

Bulletin No. 300–2–95, Issue: F, 

Dated: July 10, 2006. 

(4) For Models EA–300S and EA–

300L airplanes only: Reinforce 

the fuselage frame underneath 

the horizontal stabilizer main spar 

attachment bracket by installing 

the applicable modification kit (or 

FAA-approved equivalent parts).

(i) For Model EA–300S: Within the next 200 hours TIS after December 17, 2002 (the effective date of AD 2002–21–11) or within the 

next 100 hours TIS after February 28, 2007 (the effective date of 

this AD), whichever occurs first, unless already done. (ii) For Model 

EA–300L: Within the next 100 hours TIS after February 28, 2007 

(the effective date of this AD), unless already done.

Follow Part III of EXTRA Service 

Bulletin No. 300–2–95, Issue: F, 

Dated: July 10, 2006. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Standards Office, Small 

Airplane Directorate, FAA, ATTN: Karl 

Schletzbaum, Aerospace Engineer, 901 

Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4146; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(g) AMOCs approved for AD 2002–21–11 

are approved for this AD. 

Related Information 

(h) The European Aviation Safety Agency 

(EASA) AD No. 2006–0281, dated September 

14, 2006, also addresses the subject of this 

AD. 

Material Incorporated by Reference 

(i) You must use EXTRA Service Bulletin 

No. 300–2–95, Issue: F, Dated: July 10, 2006 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact EXTRA 

Flugzeugproduktions- und Vertriebs- GmbH, 

Schwarze Heide 21, D–46569 Huenxe, 

Germany; fax: (+49)–2858–9137–42. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Kansas City, Missouri 

64106; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri on January 

12, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–775 Filed 1–23–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24452; Directorate 

Identifier 2006–NE–11–AD; Amendment 

39–14893; AD 2007–02–06] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney PW2000 Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Pratt & 

Whitney PW2000 series turbofan 

engines. This AD requires a onetime 

focused visual and fluorescent penetrant 

inspection (FPI) of 21 suspect PW2000 

8th stage high pressure compressor 

(HPC) drum rotor disk assemblies. This 

AD results from a PW2037 8th stage 

HPC drum rotor disk assembly failure 

event caused by tooling damage that 

occurred during disk assembly 

manufacture. We are issuing this AD to 

prevent 8th stage HPC drum rotor disk 

assembly failure that could result in an 

uncontained engine failure and damage 

to the airplane. 

DATES: This AD becomes effective 

February 28, 2007. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of February 28, 2007. 

ADDRESSES: You can get the service 

information identified in this AD from 

Pratt & Whitney, 400 Main St., East 

Hartford, CT 06108; telephone (860) 

565–8770; fax (860) 565–4503. 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

Room PL–401 on the plaza level of the 

Nassif Building, 400 Seventh Street, 

SW., Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Mark Riley, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

telephone (781) 238–7758; fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to Pratt & Whitney PW2000 

series turbofan engines. We published 

the proposed AD in the Federal Register 

on August 3, 2006 (71 FR 43997). That 

action proposed to require a onetime 

focused visual and FPI of 21 suspect 

PW2000 8th stage HPC drum rotor disk 

assemblies. 


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Federal Register / Vol. 72, No. 15 / Wednesday, January 24, 2007 / Rules and Regulations 3053 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the Docket Management 

Facility Docket Office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Office (telephone (800) 647–5227) is 

located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. Comments will be available 

in the AD docket shortly after the DMS 

receives them. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Claim That AD Action Is Redundant 

Northwest Airlines and Air Transport 

Association claim that the proposed AD 

is redundant to existing requirements in 

the engine manual, and would only put 

an additional administrative burden on 

the operators. They further state that 

existing AD 2005–18–03 (enhanced 

inspection of critical rotating parts) 

already requires a focused FPI of the 

drum rotor disk and includes the area of 

question on the 8th stage disk. The 

commenters point out that the visual 

inspection referenced in Pratt & 

Whitney Alert Service Bulletin (ASB) 

No. PW2000 A72–706, dated February 

17, 2006 requires that any disk damage 

be within the limits in the engine 

manual visual inspection. 

We do not agree. The intent of this AD 

is to require inspection of the HPC 8th 

stage disk when the HPC rotor assembly 

is exposed but with compressor blades 

installed. The requirements in this AD 

are more restrictive than the 

requirements of AD 2005–18–03, which 

only requires inspection when the HPC 

rotor is removed from the HPC module 

and disassembled to the piece-part level 

with compressor blades removed. 

For clarification, we revised the AD 

compliance section to state that the 8th 

stage HPC drum rotor disk assembly is 

a rotor with compressor blades 

installed. 

Proposed AD Not Clear if the 

Nondestructive Inspection Procedures 

(NDIPs) Are Mandatory 

Northwest Airlines and Air Transport 

Association state that the proposed AD 

is not clear if the NDIPs referenced in 

the Pratt & Whitney ASB No. PW2000 

A72–706, dated February 17, 2006, are 

mandatory. 

We agree. We clarified the AD by 

splitting up the information needed in 

paragraph (f), into subparagraphs. We 

also clarified the AD by specifying to 

use paragraphs 3., 3.A., and 3.B., of the 

Accomplishment Instructions of Pratt & 

Whitney ASB No. PW2000 A72–706, 

dated February 17, 2006, to use NDIP 

1096, dated January 19, 2006, and to use 

NDIP 1095, dated January 12, 2006. 

Claim That AD Is Not Required 

Northwest Airlines states that the AD 

is not required, since all affected parts 

will be scrapped at exposure. The 

commenter states that since most of the 

affected parts in the field are likely to 

have very few cycles remaining, the 

parts will be retired upon their next 

disassembly. 

We do not agree. The estimated 

number of cycles on the affected 8th 

stage disks currently in service ranges 

from about 13,500 cycles to 19,000 

cycles. The current life limit of the 8th 

stage disk is 20,000 cycles. Therefore, 

some of the affected 8th stage disks 

probably will be returned to service 

after a shop visit. Affected parts with 

very few cycles remaining and 

voluntarily removed from service, will 

not require inspection or incur any 

inspection cost. 

Recommend Compliance Time Be 

Reduced 

The National Transportation Safety 

Board (NTSB) supports the need for a 

onetime focused visual and FPI 

inspection of the HPC 8th stage disk. 

However, the NTSB recommends that 

the compliance time be reduced due to 

unknown factors from the disk failure 

investigation (failure location striation 

count) and the disk’s demonstrated lack 

of damage tolerance. 

We do not agree. The finite element 

structural analysis performed by Pratt & 

Whitney for the 8th stage disk failure 

(PW2037 engine uncontained 8th stage 

HPC drum rotor disk assembly failure 

event, March 10, 2005,) correlate well 

with results from the Materials & 

Processes Engineering Lab 

measurements. The Lab measurements 

were of the fatigue striation counts from 

the failed disk. Based on the failure 

analysis and the manufacturing records 

review of the 8th stage disk, a risk 

analysis determined that an acceptable 

level of safety will be maintained for the 

compliance described in the AD. 

Service Documents Should Be 

Incorporated by Reference 

Modification and Replacement Parts 

Association (MARPA) states that the 

Pratt & Whitney service information 

referenced in the proposed AD should 

be incorporated by reference for the AD 

to be considered legal. 

We agree. Paragraph (i) of this AD 

incorporates by reference the necessary 

service information. The proposed AD 

did not contain the incorporation by 

reference paragraph (i), because it is 

only a notice of proposed rulemaking. 

Service Documents Should Be 

Published in the Docket Management 

System (DMS) 

MARPA states that the Pratt & 

Whitney service information to be 

incorporated by reference in the AD, 

should be published in the DMS, as it 

is part of the AD. 

We partially agree. We are currently 

reviewing issues surrounding the 

posting of service information on the 

DMS as part of an AD Docket. Once we 

thoroughly examine all aspects of this 

issue and make a final determination, 

we will consider if our current practice 

needs revising. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

15 engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 70 work-hours per engine to 

perform the actions, and that the 

average labor rate is $80 per work-hour. 

We do not expect that parts will be 

required. Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $84,000 for the 

inspection. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in subtitle VII, 

part A, subpart III, section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 


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3054 Federal Register / Vol. 72, No. 15 / Wednesday, January 24, 2007 / Rules and Regulations 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends 14 CFR part 39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2007–02–06 Pratt & Whitney: Amendment 

39–14893. Docket No. FAA–2006–24452; 

Directorate Identifier 2006–NE–11–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 28, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Pratt & Whitney 

PW2037, PW2040, and PW2037M turbofan 

engines. These engines are installed on, but 

not limited to Boeing 757 airplanes. 

Unsafe Condition 

(d) This AD results from a Pratt & Whitney 

PW2037 8th stage high-pressure compressor 

(HPC) drum rotor disk assembly failure event 

caused by tooling damage that occurred 

during disk assembly manufacture. We are 

issuing this AD to prevent 8th stage HPC 

drum rotor disk assembly failure that could 

result in an uncontained engine failure and 

damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed at the 

next shop visit, not to exceed an additional 

6,000 engine cycles, after the effective date of 

this AD, when the 8th stage HPC drum rotor 

disk assembly (compressor blades installed) 

is exposed and removed from the HPC 

module, unless the actions have already been 

done. 

Inspect the 8th Stage Drum Rotor Disk 

(f) Inspect the 8th stage drum rotor disks 

listed by part numbers and serial numbers in 

Table 1 of the Accomplishment Instructions 

of Pratt & Whitney Alert Service Bulletin No. 

PW2000 A72–706, dated February 17, 2006, 

as follows: 

(1) Do a onetime focused visual and 

fluorescent penetrant inspection (FPI) of 

suspect 8th stage HPC drum rotor disk 

assemblies that may have been damaged 

during manufacture. 

(2) Use paragraphs 3., 3.A., and 3.B. of the 

Accomplishment Instructions of Pratt & 

Whitney Alert Service Bulletin No. PW2000 

A72–706, dated February 17, 2006, 

Nondestructive Inspection Procedure (NDIP) 

1096, dated January 19, 2006, and NDIP 

1095, dated January 12, 2006, to do the 

inspections. 

(3) Any 8th stage disk damage that exceeds 

the serviceable limits specified in Pratt & 

Whitney PW2000 Engine Manual, Part 

Number 1A6231, Chapter/Section 72–35–03, 

Inspection/Check–01/–04, can not be 

returned to service. 

(g) After the effective date of this AD, do 

not install any uninspected 8th stage drum 

rotor disk assemblies listed in Table 1 of the 

Accomplishment Instructions of Pratt & 

Whitney Alert Service Bulletin No. PW2000 

A72–706, dated February 17, 2006, in any 

engine. 

Alternative Methods of Compliance 

(h) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Material Incorporated by Reference 

(i) You must use the Pratt & Whitney 

service information specified in Table 1 to 

perform the actions required by this AD. The 

Director of the Federal Register approved the 

incorporation by reference of the documents 

listed in Table 1 of this AD in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Pratt & Whitney, 400 Main St., East 

Hartford, CT 06108; telephone (860) 565–

8770; fax (860) 565–4503, for a copy of this 

service information. You may review copies 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

TABLE 1.—INCORPORATION BY REFERENCE

Pratt & Whitney service information Page Revision Date 

Alert Service Bulletin No. PW2000 A72–706 ..........................................................................

Total Pages: 11 

All ............ Original .... February 17, 2006. 

Nondestructive Inspection Procedure 1095 ............................................................................

Total Pages: 18 

All ............ Original .... January 12, 2006. 

Nondestructive Inspection Procedure 1096 ............................................................................

Total Pages: 18 

All ............ Original .... January 19, 2006. 


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Federal Register / Vol. 72, No. 15 / Wednesday, January 24, 2007 / Rules and Regulations 3055 

Relate Information 

(j) Contact Mark Riley, Aerospace Engineer, 

Engine Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

telephone (781) 238–7758; fax (781) 238–

7199, e-mail: mark.riley@faa.gov for more 

information about this AD. 

Issued in Burlington, Massachusetts, on 

January 12, 2007. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–686 Filed 1–23–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30532 Amdt. No. 3202] 

Standard Instrument Approach 

Procedures, Weather Takeoff 

Minimums; Miscellaneous 

Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This amendment establishes, 

amends, suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and/or Weather Takeoff 

Minimums for operations at certain 

airports. These regulatory actions are 

needed because of the adoption of new 

or revised criteria, or because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, addition of 

new obstacles, or changes in air traffic 

requirements. These changes are 

designed to provide safe and efficient 

use of the navigable airspace and to 

promote safe flight operations under 

instrument flight rules at the affected 

airports. 

DATES: This rule is effective January 24, 

2007. The compliance date for each 

SIAP and/or Weather Takeoff 

Minimums is specified in the 

amendatory provisions. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of January 24, 

2007. 

ADDRESSES: Availability of matters 

incorporated by reference in the 

amendment is as follows: 

For Examination—

1. FAA Rules Docket, FAA 

Headquarters Building, 800 

Independence Avenue, SW., 

Washington, DC 20591; 

2. The FAA Regional Office of the 

region in which the affected airport is 

located; 

3. The National Flight Procedures 

Office, 6500 South MacArthur Blvd., 

Oklahoma City, OK 73169 or, 

4. The National Archives and Records 

Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, 

or go to: http://www.archives.gov/ 

federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

For Purchase—Individual SIAP and 

Weather Takeoff Minimums copies may 

be obtained from: 

1. FAA Public Inquiry Center (APA–

200), FAA Headquarters Building, 800 

Independence Avenue, SW., 

Washington, DC 20591; or 

2. The FAA Regional Office of the 

region in which the affected airport is 

located. 

By Subscription—Copies of all SIAPs 

and Weather Takeoff Minimums mailed 

once every 2 weeks, are for sale by the 

Superintendent of Documents, U.S. 

Government Printing Office, 

Washington, DC 20402. 

FOR FURTHER INFORMATION CONTACT: 

Donald P. Pate, Flight Procedure 

Standards Branch (AFS–420), Flight 

Technologies and Programs Division, 

Flight Standards Service, Federal 

Aviation Administration, Mike 

Monroney Aeronautical Center, 6500 

South MacArthur Blvd., Oklahoma City, 

OK 73169 (Mail Address: P.O. Box 

25082 Oklahoma City, OK 73125) 

telephone: (405) 954–4164. 

SUPPLEMENTARY INFORMATION: This 

amendment to Title 14 of the Code of 

Federal Regulations, Part 97 (14 CFR 

part 97), establishes, amends, suspends, 

or revokes SIAPs and/or Weather 

Takeoff Minimums. The complete 

regulatory description of each SIAP 

and/or Weather Takeoff Minimums is 

contained in official FAA form 

documents which are incorporated by 

reference in this amendment under 5 

U.S.C. 552(a), 1 CFR part 51, and 14 

CFR part 97.20. The applicable FAA 

Forms are identified as FAA Forms 

8260–3, 8260–4, 8260–5 and 8260–15A. 

Materials incorporated by reference are 

available for examination or purchase as 

stated above. 

The large number of SIAPs and/or 

Weather Takeoff Minimums, their 

complex nature, and the need for a 

special format make their verbatim 

publication in the Federal Register 

expensive and impractical. Further, 

airmen do not use the regulatory text of 

the SIAPs and/or Weather Takeoff 

Minimums but refer to their depiction 

on charts printed by publishers of 

aeronautical materials. Thus, the 

advantages of incorporation by reference 

are realized and publication of the 

complete description of each SIAP and/ 

or Weather Takeoff Minimums 

contained in FAA form documents is 

unnecessary. The provisions of this 

amendment state the affected CFR 

sections, with the types and effective 

dates of the SIAPs and/or Weather 

Takeoff Minimums. This amendment 

also identifies the airport, its location, 

the procedure identification and the 

amendment number. 

The Rule 

This amendment to 14 CFR part 97 is 

effective upon publication of each 

separate SIAP and/or Weather Takeoff 

Minimums as contained in the 

transmittal. Some SIAP and/or Weather 

Takeoff Minimums amendments may 

have been previously issued by the FAA 

in a Flight Data Center (FDC) Notice to 

Airmen (NOTAM) as an emergency 

action of immediate flight safety relating 

directly to published aeronautical 

charts. The circumstances which 

created the need for some SIAP, and/or 

Weather Takeoff Minimums 

amendments may require making them 

effective in less than 30 days. For the 

remaining SIAPs and/or Weather 

Takeoff Minimums, an effective date at 

least 30 days after publication is 

provided. 

Further, the SIAPs and/or Weather 

Takeoff Minimums contained in this 

amendment are based on the criteria 

contained in the U.S. Standard for 

Terminal Instrument Procedures 

(TERPS). In developing these SIAPs 

and/or Weather Takeoff Minimums, the 

TERPS criteria were applied to the 

conditions existing or anticipated at the 

affected airports. Because of the close 

and immediate relationship between 

these SIAPs and/or Weather Takeoff 

Minimums and safety in air commerce, 

I find that notice and public procedure 

before adopting these SIAPs and/or 

Weather Takeoff Minimums are 

impracticable and contrary to the public 

interest and, where applicable, that 

good cause exists for making some 

SIAPs and/or Weather Takeoff 

Minimums effective in less than 30 

days. 

Conclusion 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. It, therefore—(1) is not a 

‘‘significant regulatory action’’ under 

Executive Order 12866; (2) is not a 


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